Methods and systems for requesting and retrieving aircraft data during flight of an aircraft

ABSTRACT

The disclosed embodiments relate to methods and systems for requesting and retrieving aircraft data during flight of an aircraft. This aircraft data can be used to perform additional monitoring of aircraft sub-systems to detect an abnormal condition, and/or to identify one or more sources that are causing the abnormal condition. In one embodiment, aircraft data for one or more relevant parameters can be requested from the ground, measured on-board the aircraft, and stored in a data file that is then communicated back to personnel on the ground. The real-time aircraft data for one or more relevant parameters can then be analyzed to identify the one or more sources that are causing the abnormal condition.

TECHNICAL FIELD

Embodiments of the present invention generally relate to aircraft, andmore particularly relate to methods and systems for requesting andretrieving aircraft data during flight of an aircraft.

BACKGROUND OF THE INVENTION

When an aircraft is in flight, it can be difficult to detect whensub-systems or components of an aircraft begin to operate abnormally,and/or to correctly diagnose the specific source that is causing thatsub-system or component to operate abnormally. While these abnormaloperating conditions may persist after the aircraft has landed, in manycases they do not, which can make it even more difficult to correctlydiagnose the specific source that is causing that sub-system orcomponent to operate abnormally.

There is a need for methods and systems for monitoring the health of anaircraft and the aircraft's various components and sub-systems. It wouldbe desirable to provide methods and systems that can automaticallydetect abnormal conditions that indicate when one or more sub-systems orcomponents of an aircraft have experienced degradation in performance.It would also be desirable if such methods and systems can identify thespecific source(s) within those particular sub-systems or componentsthat are causing the degradation in performance so that correctiveactions can be taken with respect to the identified sub-systems orcomponents prior to fault indication or failure. It would also bedesirable if such methods and systems execute automatically and do notrequire flight crew intervention. It would also be desirable to providemethods and systems that allow for ground personnel to request, collectand communicate aircraft data during flight of an aircraft. Otherdesirable features and characteristics of the present invention willbecome apparent from the subsequent detailed description and theappended claims, taken in conjunction with the accompanying drawings andthe foregoing technical field and background.

SUMMARY

In one embodiment, a method is provided in which relevant parametersthat are to be measured on-board the aircraft can be determined. Aparameter request message is then generated that includes a parameterfile that specifies the relevant parameters that are to be measured atthe aircraft. The parameter request message is communicated to theaircraft over satellite communication links, and data for each relevantparameter is measured and recorded in a data file that is thencommunicated from the aircraft to the other computer that is coupled tothe ground-based computer for further analysis

In another embodiment, a system is provided. The system includes anaircraft, a satellite that is communicatively coupled to the aircraftand a gateway via satellite communication links, a ground supportnetwork comprising a ground-based computer, and another computer,coupled to the ground-based computer, that is configured to generate aparameter request message. The parameter request message includes aparameter file that specifies relevant parameters that are to bemeasured at the aircraft. The parameter request message can becommunicated to the gateway for transmission to the aircraft oversatellite communication links. The aircraft comprises an on-boardcomputer, and a transceiver. The on-board computer is configured tomeasure data for each relevant parameter of the parameter file and torecord the measured data in a data file. The transceiver is configuredto transmit the data file to the satellite for delivery to the othercomputer.

DESCRIPTION OF THE DRAWINGS

Embodiments of the present invention will hereinafter be described inconjunction with the following drawing figures, wherein like numeralsdenote like elements, and

FIG. 1 illustrates an integrated system for aircraft health and trendmonitoring of an aircraft and the aircraft's various sub-systems inaccordance with some of the disclosed embodiments.

FIG. 2A is an exemplary perspective view of an aircraft that can be usedin accordance with some of the disclosed embodiments.

FIG. 2B is a functional block diagram of an Aircraft Health and TrendMonitoring (AHTM) system in accordance with an exemplary implementationof the disclosed embodiments.

FIG. 2C is a block diagram of some of an aircraft's various sub-systemsin accordance with an exemplary implementation of the disclosedembodiments.

FIG. 3 is a block diagram of portions of a ground support network inaccordance with one exemplary implementation of the disclosedembodiments.

FIG. 4 is a flowchart of a method for requesting and retrieving aircraftdata from an aircraft's various sub-systems during flight in accordancewith one exemplary implementation of some of the disclosed embodiments.

FIG. 5A is a flowchart of a method for requesting and retrievingaircraft data from an aircraft's various sub-systems during flight inaccordance with one exemplary implementation of some of the disclosedembodiments.

FIG. 5B is a flow diagram that shows some of the processing steps andcommunication of the various messages in accordance with one exemplaryimplementation of the method of FIG. 5A.

DESCRIPTION OF EXEMPLARY EMBODIMENTS

As used herein, the word “exemplary” means “serving as an example,instance, or illustration.” The following detailed description is merelyexemplary in nature and is not intended to limit the invention or theapplication and uses of the invention. Any embodiment described hereinas “exemplary” is not necessarily to be construed as preferred oradvantageous over other embodiments. All of the embodiments described inthis Detailed Description are exemplary embodiments provided to enablepersons skilled in the art to make or use the invention and not to limitthe scope of the invention which is defined by the claims. Furthermore,there is no intention to be bound by any expressed or implied theorypresented in the preceding technical field, background, brief summary orthe following detailed description.

FIG. 1 is an integrated system 100 for health and trend monitoring of anaircraft 110 and the aircraft's various sub-systems in accordance withsome of the disclosed embodiments. As used herein, the term “healthmonitoring” refers to the process of collecting and evaluating relevantparameters and/or measured data to determine the state, status, ornumerical output value of a component and/or sub-system in any timeperiod. As used herein, the term “trend monitoring” refers to theprocess of collecting and evaluating relevant parameters and/or measureddata to determine the state, status, or numerical output value of acomponent and/or sub-system in any time period in order to predict,estimate, or trend, said state, status, or numerical output value of acomponent and/or sub-system at a future time.

The system 100 includes an aircraft 110, a satellite 112 that iscommunicatively coupled to the aircraft 110 and a gateway 114 viasatellite communication links 111, 113, a ground support network 116that includes at least one ground-based computer 117 (FIG. 1 illustratesan exemplary implementation with eleven computers 117-1 thorough117-11), and another computer 122 that is coupled to the ground supportnetwork 116 via server 118. The computer 122 may be located, forexample, at aircraft monitoring center of either an operator or theaircraft manufacturer.

While in flight, the aircraft 110 can transmit data over a satellitecommunication link 111. For example, in one embodiment, the datatransmitted by the aircraft while in flight comprises a crew alertingsystem (CAS) message generated by the on-board computer (not shown inFIG. 1) of the aircraft. To explain further, many modern aircraft useCrew Alerting System (CAS) messages to provide engine and aircraftsystem fault information to the crew. CAS messages are annunciated tothe crew based on triggers and logic embedded in an avionics suite. Thelogic typically receives inputs from all reporting aircraft systems andsub-systems. A CAS message is triggered when the combination of receivedinputs meets predetermined criteria of embedded logic. This could beBoolean or binary type inputs, or floating point parameters. Once thelogic criteria have been satisfied, the avionics suite displays amessage to the crew in either Red (warning), Amber (caution), or Cyan(advisory). Many CAS messages display failure or fault information tothe crew. In these instances when failure or fault information isdisplayed, it is assumed that the system has experienced an anomaly anda corrective action must be performed to successfully extinguish the CASmessage. The system records all of the CAS parameters at any given time.The CAS parameter value of the message has a zero value until the CASmessage becomes active. Once active, the value of the CAS parametervalue changes from zero to an integer between one (1) and sixty-three(63) depending on what failed. As the CAS messages are recorded, thesystem is detects when the value of the parameter changes from zero to anon-zero value.

The CAS message includes unprocessed data. The CAS message automaticallyindicates that measured data for a relevant parameter or variable of asub-system of the aircraft is outside one or more threshold limits andthat an abnormal condition has been detected. In accordance with some ofthe disclosed embodiments, when a CAS message is generated on-board theaircraft 110, data for parameters that are associated with thatparticular CAS message are automatically measured and stored in a filethat is transmitted to the ground support network 116. Aircraftmaintenance and engineering personnel can determine based on experiencea number of different parameters that are the typical triggers for eachparticular CAS message. As such, for each particular CAS message,parameters and their respective thresholds (e.g., upper and/or lowerthresholds for each parameter) can be pre-defined.

The aircraft on-board computer is configured to open a communicationpath that includes a first satellite communication link 111 between theaircraft 110 and the satellite 112 and a second satellite communicationlink 113 between the satellite 112 and the ground-based gateway 114. Assuch, the satellite 112 is communicatively coupled to the aircraft 110and to the gateway 114 via satellite communication links 111, 113,respectively, and any servers between the aircraft 110 and the gateway114. The on-board computer of the aircraft 110 can communicate the CASmessage file over the first satellite communication link 111 to thesatellite 112. The satellite 112 can then communicate the CAS messagefile over the second satellite communication link 113 to the gateway114, and the gateway 114 can communicate the CAS message file to theground support network 116 via communication link 115.

The ground support network 116 can be operated by a different party orentity from the party or entity operating the aircraft. The groundsupport network 116 includes several health management algorithms thatare used to process data and data files received from the aircraft 110.Once the data from the aircraft 110 is processed using the appropriatehealth management algorithms, the ground support network 116 cangenerate web pages that are provided to the server 118. The web pagesinclude information regarding aircraft health and/or fleet health. Theweb pages can include the processed data generated from unprocessed datacommunicated from the aircraft 110, data files from the aircraft 110,information derived from the processed data or data files, etc. The webpages can also include information that identifies elements of theaircraft, such as sub-systems (or components thereof), which need to beinspected.

In accordance with the disclosed embodiments, the ground support network116 includes at least one ground-based computer 117 (eleven computers117-1 . . . 117-11 are illustrated in the exemplary implementation ofFIG. 1). In one exemplary, non-limiting embodiment, the ground-basedcomputer 117 of the ground support network 116 is configured to processthe unprocessed data from the CAS message file that was transmitted fromthe aircraft 110 to generate the processed data. For example, when thefile corresponding to the CAS message is received and loaded at one ofthe ground-based computers 117 of the ground support network 116, theground-based computer 117 may load and execute an appropriate AircraftHealth and Trend Monitoring (AHTM) program module (380 in FIG. 3) thatcorresponds to the particular CAS message indicated in the file. Whenthe ground-based computer 117 executes a Health and Trend MonitoringAlgorithm (HTMA), the measured data for each of the parameters that areincluded in the file can be analyzed to determine which of theparameters are at an abnormal level (i.e., outside of its upper and/orlower threshold limits), and thus most likely causing that particularCAS message to be generated. For example, in some embodiments, each ofthe parameters can be compared to one or more thresholds, and anyparameters that are determined to be outside those threshold(s) can beidentified as being a potential cause of the CAS message. When themeasured data for any parameter is determined to be abnormal, the HTMAcan flag the abnormality and the parameters that are outside of theirrespective threshold(s) can then be stored in as processed data in aprocessed data file. In some implementations, the processed data canalso indicate particular sub-system(s) (or components thereof) that eachof the parameters are associated with. This way, those particularsub-system(s) (or components thereof) can be identified and flagged forfurther inspection to determine whether they are operating correctly orwhether corrective actions need to be taken.

The ground support network 116 is coupled to the server 118 via acommunication link 125. The server 118 serves as a portal to the groundsupport network 116, and serves the web pages from the ground supportnetwork 116 to the computer 122 so that the web pages can be displayed.Among other information, the ground-based computer 117 can communicatethe processed data (that was generated from the unprocessed datareceived from the aircraft 110) to the server 118 via these web pages.

The computer 122 is coupled to the ground support network 116 via acommunication link 119 to the server 118. The computer 122 allowscommunication to the ground support network 116, for example from asystem operator and/or another computer system, and can be implementedusing any suitable method and apparatus. This way, the informationgenerated at the ground support network 116 can be viewed by personnelor operator at the computer 122. The computer 122 can include one ormore network interfaces to communicate to other systems or components,one or more terminal interfaces to communicate with technicians, and oneor more interfaces to connect to the ground support network 116.

In accordance with the disclosed embodiments, the server 118communicates the processed data to the other computer 122.

Although not illustrated in FIG. 1, the computer 122 includes aprocessor that can perform processing, either automatically or inresponse to input from an operator, to generate a parameter requestmessage. In some scenarios, the processing can be performed based on orin response to processed data that was generated based on data receivedfrom the aircraft 110 while in flight.

The parameter request message includes a parameter file that specifiesrelevant parameters that have been selected to be measured and recordedat the aircraft 110 to provide the additional parametric data. In someembodiments, the parameter file also includes a duration value for eachrelevant parameter. Each duration value specifies how long parametricdata for that particular relevant parameter are to be measured andrecorded.

In accordance with one non-limiting, exemplary embodiment, the relevantparameters can be selected either automatically by software or by ahuman operator.

In one embodiment, the relevant parameters are determined based onanalysis of the processed data either automatically by software or by ahuman operator that analyzes the processed data. Each of the relevantparameters can correspond to additional parametric data that is neededfrom the aircraft 110 to identify one or more sources that are causingan abnormal condition (e.g., that caused the CAS message to begenerated). In some implementations, each relevant parameter caninfluence or affect data that is to be measured by the aircraft.

For example, in some embodiments, the relevant parameters can bedetermined using computer software that is implemented at a computer toautomatically analyze the processed data to automatically determinerelevant parameters that are to be measured at the aircraft to providethe additional data. By contrast, in some other embodiments, therelevant parameters can be determined by an operator on any basis,observation or information. For instance, in one implementation, theoperator might, for example, view the processed data via a computerinterface and manually identify and select relevant parameters atcomputer 122 based on the processed data.

Regardless of how the parameter request message is generated, thecomputer 122 communicates the parameter request message to the server118, which communicates the parameter request message to the groundsupport network 116. The ground support network 116 then communicatesthe parameter request message to the gateway 114, which communicates theparameter request message to the satellite 112 via the second satellitecommunication link 113. The satellite 112 then communicates theparameter request message to the aircraft 110 via the first satellitecommunication link 111.

As discussed in more detail below, the aircraft 110 includes at leastone an on-board computer and a transceiver and wireless communicationnetwork interface for communicating information over the satellitecommunication link 111. After receiving the parameter request message,the on-board computer is configured to extract the parameter file fromthe parameter request message at the on-board computer of the aircraft110, to determine the relevant parameters (and optionally thecorresponding duration values for each of the relevant parameters fromthe parameter file), and to measure parametric data for each relevantparameter for a corresponding duration value and to record the measuredparametric data in a data file. In some implementations, the measuredparametric data for each of the relevant parameters comprises a datastream of measured parametric data for that particular relevantparameter that is measured for a particular corresponding durationvalue.

The transceiver is configured to transmit the data file over the firstsatellite communication link 111 to the satellite 112 for delivery tothe ground support network 116 and to the other computer 122.

In one embodiment, upon receiving the data file, the satellite 112communicates the data file over the second satellite communication link113 to the gateway 114, and the gateway 114 communicates the data fileto the ground support network 116. The ground support network 116 canthen communicate the data file to the server 118, which can communicatethe data file to the computer 122 for display on a computer interface.

FIG. 2A is a perspective view of an aircraft 110 that can be used inaccordance with some of the disclosed embodiments. In accordance withone non-limiting implementation of the disclosed embodiments, theaircraft 110 includes a fuselage 205, two main wings 201-1, 201-2, avertical stabilizer 212, an elevator 209 that includes two horizontalstabilizers 213-1 and 213-2 in a T-tail stabilizer configuration, andtwo jet engines 211-1, 211-2. For flight control, the two main wings201-1, 201-2 each have an aileron 202-1, 202-2, an aileron trim tab206-1, 206-2, a spoiler 204-1, 204-2 and a flap 203-1, 203-2, while thevertical stabilizer 212 includes a rudder 207, and the aircraft'shorizontal stabilizers (or tail) 213-1, 213-2 each include an elevatortrim tab 208-1, 208-2. Although not shown in FIG. 2A, the aircraft 110also includes an onboard computer, aircraft instrumentation and variouscontrol systems and sub-systems as will now be described with referenceto FIG. 2B.

FIG. 2B is a block diagram of an Aircraft Health and Trend Monitoring(AHTM) system 200 in accordance with an exemplary implementation of thedisclosed embodiments. Part of the system 200 is implemented within anaircraft 110 for acquiring data. This data can include measured data forone or more relevant variables, measured data for relevant parametersassociated with the one or more relevant variables, CAS messages andmeasured data for relevant parameters associated with the one or moreCAS messages. This data can then be communicated from the aircraft 110to the ground support network 116 and used for monitoring the health ofone or more elements (e.g., sub-systems 230 or components of suchsub-systems) of the aircraft 110, and/or for monitoring trendingbehavior exhibited by one ore more elements of the aircraft 110. Asshown, the system 200 includes various sub-systems 230 of the aircraft110.

The aircraft 110 portion of the system 200 includes an onboard computer210, various sub-systems 230, aircraft instrumentation 250, cockpitoutput devices 260 (e.g., display units 262 such as control displayunits, multifunction displays (MFDs), etc., audio elements 264, such asspeakers, etc.), and various input devices 270 such as a keypad whichincludes a cursor controlled device, and one or more touchscreen inputdevices which can be implemented as part of the display units.

The aircraft instrumentation 250 can include, for example, an airspeeddata system, elements of a Global Position System (GPS), which providesGPS information regarding the position and/or speed of the aircraft, andelements of an Inertial Reference System (IRS), proximity sensors,switches, relays, video imagers, etc. In general, the IRS is aself-contained navigation system that includes inertial detectors, suchas accelerometers, and rotation sensors (e.g., gyroscopes) toautomatically and continuously calculate the aircraft's position,orientation, heading (direction) and velocity (speed of movement)without the need for external references once the IRS has beeninitialized.

The onboard computer 210 includes a data bus 215, a processor 220,system memory 223, and satellite communication transceivers and wirelesscommunication network interfaces 271.

The data bus 215 serves to transmit programs, data, status and otherinformation or signals between the various elements of FIG. 2B. The databus 215 is used to carry information communicated between the processor220, the system memory 223, the various sub-systems 230, aircraftinstrumentation 250, cockpit output devices 260, various input devices270, and the satellite communication transceivers and wirelesscommunication network interfaces 271. The data bus 215 can beimplemented using any suitable physical or logical means of connectingthe on-board computer 210 to at least the external and internal elementsmentioned above. This includes, but is not limited to, direct hard-wiredconnections, fiber optics, and infrared and wireless bus technologies.

The processor 220 performs the computation and control functions of thecomputer system 210, and may comprise any type of processor 220 ormultiple processors 220, single integrated circuits such as amicroprocessor, or any suitable number of integrated circuit devicesand/or circuit boards working in cooperation to accomplish the functionsof a processing unit.

It should be understood that the system memory 223 may be a single typeof memory component, or it may be composed of many different types ofmemory components. The system memory 223 can includes non-volatilememory (such as ROM 224, flash memory, etc.), memory (such as RAM 225),or some combination of the two. The RAM 225 can be any type of suitablerandom access memory including the various types of dynamic randomaccess memory (DRAM) such as SDRAM, the various types of static RAM(SRAM). The RAM 225 includes an operating system 226, and data filegeneration programs 228. The RAM 225 stores executable code for one ormore data file generation programs 228. The data file generationprograms 228 (stored in system memory 223) that can be loaded andexecuted at processor 220 to implement a data file generation module 222at processor 220. As will be explained below, the processor 220 executesthe data file generation programs 228 to generate data files thatinclude measured parametric data that is used at the ground supportnetwork 116 and/or computer 122 to conducting health and trendmonitoring for one or more aircraft sub-systems (or components thereof).

In addition, it is noted that in some embodiments, the system memory 223and the processor 220 may be distributed across several differenton-board computers that collectively comprise the on-board computersystem 210.

The satellite communication transceivers and wireless communicationnetwork interfaces 271 are operatively and communicatively coupled tosatellite antenna 272 that can be external to the on-board computer 210.The satellite antenna 272 that can be used to communicate informationwith the satellite 112 over a satellite communication links 111 and 113.The satellite gateway 114 can be coupled to other networks, includingthe Internet, so that information can be exchanged with remotecomputers.

FIG. 2C is a block diagram of various sub-systems 230 of an aircraft 110in accordance with an exemplary implementation of the disclosedembodiments.

In one exemplary, non-limiting implementation, the various sub-system(s)231-246 include a thrust reverser control sub-system(s) 231, a brakecontrol sub-system(s) 232, a flight control sub-system(s) 233, asteering control sub-system(s) 234, aircraft sensor controlsub-system(s) 235, an auxiliary power unit (APU) inlet door controlsub-system(s) 236, a cabin environment control sub-system(s) 237, alanding gear control sub-system(s) 238, propulsion sub-system(s) 239,fuel control sub-system(s) 240, lubrication sub-system(s) 241, groundproximity monitoring sub-system(s) 242, aircraft actuator sub-system(s)243, airframe sub-system(s) 244, avionics sub-system(s) 245, softwaresub-system(s) 246.

The sub-system(s) 231-246 that are illustrated in FIG. 2B are exemplaryonly, and in other embodiments various other sub-system(s) can beincluded such as, for example, air data sub-system(s), auto flightsub-system(s), engine/powerplant/ignition sub-system(s), electricalpower sub-system(s), communications sub-system(s), fire protectionsub-system(s), hydraulic power sub-system(s), ice and rain protectionsub-system(s), navigation sub-system(s), oxygen sub-system(s), pneumaticsub-system(s), information sub-system(s), exhaust sub-system(s), etc.

Although not illustrated in FIG. 2C, those skilled in the art willappreciate that each of the various sub-systems can include one or morecomponents. In addition, each of the various sub-systems can eachinclude one or more sensors to facilitate measurement and generation ofdata pertaining to operation of that sub-system of the aircraft 110(and/or a component of that sub-system), to assist in performingdiagnostics and health monitoring of one or more sub-systems, etc. Eachsensor can generate data that is used to generate information that canbe included in the parameter files that are generated by the data filegeneration unit 222 of FIG. 2B.

In general, a “sensor” is a device that measures a physical quantity andconverts it into a signal which can be read by an observer or by aninstrument. In general, sensors can be used to sense light, motion,temperature, magnetic fields, gravitational forces, humidity, vibration,pressure, electrical fields, current, voltage, sound, and other physicalaspects of an environment. Non-limiting examples of sensors can includeacoustic sensors (e.g., sound, microphone, seismometer, accelerometer,etc.), vibration sensors, aircraft or other vehicle sensors (e.g., airspeed indicator, altimeter, attitude indicator, gyroscope, inertialreference unit, magnetic compass, navigation instrument sensor, speedsensors, throttle position sensor, variable reluctance sensor,viscometer, wheel speed sensor, Yaw rate sensor, etc.), chemicalsensors/detectors, electric current sensors, electric potential sensors,magnetic sensors, radio frequency sensors, environmental sensors, fluidflow sensors, position, angle, displacement, distance, speed,acceleration sensors (e.g., accelerometer, inclinometer, positionsensor, rotary encoder, rotary/linear variable differential transformer,tachometer, etc.), optical, light, imaging sensors (e.g., charge-coupleddevice, infra-red sensor, LED, fiber optic sensors, photodiode,phototransistors, photoelectric sensor, etc.), pressure sensors andgauges, strain gauges, torque sensors, force sensors piezoelectricsensors, density sensors, level sensors, thermal, heat, temperaturesensors (e.g., heat flux sensor, thermometer, resistance-basedtemperature detector, thermistor, thermocouple, etc.),proximity/presence sensors, etc.

FIG. 3 is a block diagram of portions of a ground support network (GSN)116 in accordance with one exemplary implementation of the disclosedembodiments. As illustrated in FIG. 3, the ground support network 116includes at least one processor 390 (e.g., implemented at one or moreservers), memory 392 and communication interfaces 393 that are coupledto various different communication links. Although not illustrated, insome implementation, the GSN 116 can include multipleservers/processors. One such server/processor can be used for processingof inbound satellite communications and generation of outbound messagesto be communicated via outbound satellite communications destined forthe aircraft.

The memory 392 can be implemented using any of the memory technologiesthat are disclosed herein. The memory 392 stores a plurality of AircraftHealth and Trend Monitoring (AHTM) program modules 380 that can beloaded and executed at the processor 390. Each of the AHTM programmodules 380 are programmed with computer executable instructions forimplementing a particular health and trend monitoring algorithm (HTMA).The memory 392 can store various different AHTM program modules 380 thatcan be used to implement various different HTMAs via computer executableinstructions. Various examples of AHTM program modules 380 andcorresponding HTMAs will be described below.

The memory 392 can also store CAS message files 310 received from theaircraft 110, processed data 320 that is generated from the CAS messagefiles 310 after being processed by the processor 390, parameter files340 that are provided from the computer 122, and data files 370 that arereceived from the aircraft 110.

When CAS message files 310 and/or data files 370 are received at theground support network 116 from the aircraft 110, CAS message files 310and/or data files 370 can be loaded at the processor 390 along with acorresponding AHTM program module 380 that corresponds to thatparticular type of CAS message file 310 and/or data file 370. When theprocessor 390 executes the computer executable code of an AHTM programmodule 380 with respect to measured data included in the CAS messagefile 310 and/or data file 370, an instantiation of an Aircraft Healthand Trend Monitoring (AHTM) processor is implemented at the processor390.

Each parameter file 340 can include one or more relevant parameters thatare selected or identified based on the CAS message file 310. Each ofthe data files 370 can include measured data corresponding to therelevant parameters specified in the parameter file. The relevantparameters included in one of the data files 370, as well as thresholds(e.g., upper and/or lower thresholds) for each of the relevantparameters, are configurable and can be pre-defined. As will beexplained below, the measured data for each of the relevant parametersincluded in one of the data files 370 can be associated with theparticular sub-system or component of the aircraft 110, and can be usedat the ground support network 116 or the computer 122 to help analyzethe performance or operational characteristics of that particularsub-system or component, and/or to isolate the specific cause(s) of anabnormality. For example, the AHTM program modules 380 and theircorresponding HTMAs can examine measured data for relevant parameters(RPs) to determine which particular sub-system of an aircraft (or of acomponent of a particular sub-system) is most likely causing theabnormality that generated the CAS message. This way, those particularsub-system(s) (or components thereof) can be easily identified forfurther inspection to determine whether they are operating correctly orwhether corrective actions need to be taken.

FIG. 4 is a flowchart of a method 400 for requesting and retrievingaircraft data from an aircraft's various sub-systems during flight inaccordance with one exemplary implementation of some of the disclosedembodiments.

Block 401 is optional and is therefore illustrated in dashed lines. At401, in one exemplary and non-limiting embodiment, data received from anaircraft that is in flight is processed and the processed data isprovided to a computer interface of a ground-based computer. Prior to402, relevant parameters that are to be measured can be determinedand/or specified at the ground-based computer or other computer (eitherautomatically or by a human operator). In one implementation, theseadditional relevant parameters that are to be measured can be determinedand/or specified at the ground-based computer or other computer based onor taking into account the processed data.

At 402, a parameter request message is transmitted to the aircraft overa satellite communication link. The parameter request message includes aparameter file that specifies additional relevant parameters that are tobe measured and optionally specifies the duration for which eachadditional relevant parameter is to be measured.

At 403, aircraft data for each relevant parameter is measured for aspecified amount of time and recorded in a data file that is transmittedfrom the aircraft 110 back to the ground-based computer, where it can beforwarded to a computer 122. Once the data file is received at thecomputer 122, it can be processed either automatically by software ormanually to determine whether the measured data is within one or morethreshold limits or is trending away from a normal value. In someembodiments, an abnormal condition is detected when the measured data isdetermined to be outside of the one or more threshold limits.Information comprising each of the particular relevant parameters thatare determined to have measured data that is outside of the particularthreshold associated with that particular relevant parameter can then beanalyzed to determine what source(s) are causing the measured data to beoutside one or more threshold limits.

One exemplary implementation of method 400 will be described below withreference to FIGS. 5A and 5B. It is noted that in the non-limiting,exemplary implementation that is illustrated in FIGS. 5A and 5B, steps505 through 520 are optional and illustrated to show one possibleimplementation in which the triggering event for determining relevantparameters and generating a parameter file is the receipt of a CASmessage at the GSN 116. It should be appreciated that the trigger forstep 525 is not limited to this specific example, and that other eventscan cause steps 525 through 540 to be performed. In this regard, it isnoted that a wide variety of events could trigger events 525, 530 and540 that are described below, and that the receipt of a CAS message (orprocessed data from a CAS message at computer 122 prior to event 525) isonly one particular non-limiting example. A CAS message does not have tobe the trigger to perform the data request. In some implementations, atrigger event is not even required. Data can be requested from theaircraft by a person at any time during the flight, with or without aCAS message annunciating. For example, an operator at computer 122 couldrandomly decide to determine relevant parameters and generate aparameter file for transmission to the aircraft.

FIG. 5A is a flowchart of a method for requesting and retrievingaircraft data from an aircraft's various sub-systems during flight inaccordance with one exemplary implementation of some of the disclosedembodiments. FIG. 5B is a flow diagram of the method 500 of FIG. 5A thatshows some of the processing steps and communication of the variousmessages in accordance with one exemplary implementation. FIG. 5B willbe described below in conjunction with FIG. 5A, and the method 500 ofFIGS. 5A and 5B will be described below with reference to FIGS. 1through 3 to explain how the method 500 could be applied in the contextof one exemplary, non-limiting environment and operational scenario.

As noted above, events at 505, 510, 515, 520 are optional and aretherefore illustrated in dashed lines. In one particular non-limitingexample, it is presumed that prior to the start of method 500, anaircraft 110 is in flight, and an on-board computer 220 of the aircraft110 is in a monitoring state in which it monitors and waits to receive acrew alerting system (CAS) message. The CAS message triggers anannouncement to the flight crew of the aircraft, and automaticallyindicates that a relevant parameter or variable is outside of itsthreshold(s). For example, in some implementations, certain logicalbits, which indicate failures can be logically processed (e.g., arelogically AND-ed and OR-ed) in the avionics software to define when aCAS message is annunciated in the aircraft cockpit. These bits, ingeneral, indicate an abnormal condition. A CAS message necessarilyindicates that a measured parameter or variable is outside one or morethreshold limits (e.g., is above or below expected values), and thusindicates that an abnormal condition has been detected (e.g.,detects/identifies/observes an abnormality in that sub-system).

At event 505, the on-board computer 220 of the aircraft 110 generatesdata intended for transmission to the GSN 116. In one implementation,this data can be a CAS message file. When the CAS message file isgenerated, unprocessed data for each one of a set of parameters that areassociated with that particular CAS message are measured and recorded ina CAS message file corresponding to that CAS message. Each particularparameter can have a parameter name associated with it for easyidentification. The data for each particular parameter is unprocessed orraw data. With respect to any CAS message, a data stream can be measuredfor the parameter(s) for a particular duration of time based on theinitial trigger event (that caused the CAS message to be generated). TheCAS message file is typically a small file that includes some relevantparameters measured over a relatively short duration of time.

Upon generating the CAS message file, at 510, the aircraft 110 performsoperations to open a first satellite communication link 111 between theaircraft 110 and the satellite 112 and a second satellite communicationlink 113 between the satellite 112 and a ground-based gateway 114. Onceset up, the aircraft 110 then transmits the CAS message over thesatellite communication link 111 to a satellite 112. The satellite 112then relays the CAS message file over another satellite communicationlink 113 to the gateway 114. In one exemplary embodiment, the gatewaycan be an Iridium ground station. The gateway 114 then forwards the CASmessage file to the ground support network 116. The gateway 114 can thencommunicate the CAS message file to a ground-based computer of theground support network 116. The ground support network 116 is typicallyimplemented a third-party site.

In some implementations, the CAS messages can have different priorities.In one embodiment, only high priority CAS messages and their associatedCAS message files (with parameters) are immediately sent (i.e., shortlyafter generation of the CAS message file) to the ground support network116 via a satellite communication link 111 during flight of the aircraft110 before the aircraft lands. As used herein, the term high priorityrefers to a CAS message it has priority greater than other types of CASmessages. In some embodiments, a system administrator can select whichparticular CAS messages are to be designated as high priority CASmessages. In other words, the list of CAS messages are high priority CASmessages can be configured, for example, by an operator, such as, anoperator at the ground support network 116 or other computer 122; by amanufacturer of the aircraft, or any other entity. Lower priority CASmessages and their associated CAS message files can be transmitted tothe ground support network 116 when the aircraft lands via, for example,a WLAN communication link or a cellular communication link.

At 515, a ground-based computer at the ground support network 116processes the unprocessed data that was transmitted with the CAS messagefile from the aircraft 110 (while it is in flight) to generate theprocessed data from the CAS message file. For example, the groundsupport network 116 can receive the unprocessed data, uncompresses theunprocessed data from one format into another format that is readableand usable, and then process it for eventual use at the computer 122. Asone example of the processing that can be performed, the ground supportnetwork 116 can determine whether the measured data for the parametersis within one or more threshold limits. The threshold limits can be, forexample, state thresholds (e.g., binary 0 or binary 1); time thresholds(either being less than or more than a specific time), data thresholdsof data (e.g., being less than or more than a specific value of data),parameter value thresholds, etc. It is noted that although data from theCAS message file can be processed at the GSN (event 515), in otherimplementations, data from the CAS message file can be processed atother computers including a computer on-board the aircraft prior totransmission of the CAS message file. In such an implementation, the CASmessage file would include the processed data, in which cast the GSN 116simply relays the processed data to server 118.

At 520 the processed data is communicated to a computer 122 that iscoupled to the ground-based computer 117. In one implementation, theprocessed data is communicated from a ground-based computer of theground support network 116 to a server 118 that serves as a portal tothe ground support network 116. The server 118 then communicates theprocessed data to the computer 122. for display on a user interface.

In some embodiments, at event 520, the ground support network 116 canprocess the measured data for the parameters that were included in theCAS message file to determine/identify/isolate one or more underlyingcause(s) of the abnormality or abnormal condition that may have been thecause of the CAS message. To do so, in one embodiment, each parametercan be analyzed to determine which parameters have measured values thatlie outside their corresponding thresholds (i.e., are not within theirexpected values). When the measured data for that particular parameteris outside of one or more threshold limits (e.g., greater than or lessthan one ore more of the threshold limits), that parameter is loggedalong with an indication of the sub-system that it applies (for example,in an identification file). Further, in some implementations, a list ofelements can be generated that need to be inspected for potentialcorrective actions to resolve the abnormality. For example, in oneimplementation, personnel can inspect the elements that are included inthe inspection file to determine what corrective actions (if any) needto be taken to resolve the abnormality restore the elements that are thecause (or potential cause) of the abnormality (with respect toanticipated or normal operating conditions) before the abnormalitybecomes significant. In some embodiments, the information can bedisplayed on a display.

However, in some cases, the unprocessed data provided in the CAS messagefile and/or the processed data from the CAS message file will not beadequate, and it would be desirable to obtain other additionalinformation to properly assess the source or situation that caused theCAS message to be generated. For example, in many cases, the measureddata for the parameters in the CAS message file are not adequate todetermine the source (e.g., particular sub-system(s) or componentthereof) of the abnormality that caused the CAS message to be generated.Therefore it would be desirable to have a mechanism that would allowmeasured data for other relevant parameters to be requested. This canhelp ground crews determine (more precisely) what elements need to beinspected for potential corrective actions to resolve the abnormalitybefore the abnormality becomes significant

As such, in accordance with some of the disclosed embodiments, uponreceiving the processed data from the CAS message file at computer 122,it can be determined (e.g., either automatically by software or by ahuman operator) whether or not additional data or information is neededfrom the aircraft 110 to properly assess the situation that caused theCAS message to be generated. In some embodiments, by analyzingunprocessed data and/or the processed data from the CAS message file,additional relevant parameters that are needed can be determined.

Therefore, at event 525, additional relevant parameters that are to bemeasured or generated at the aircraft are determined.

For example, in one implementation, the additional relevant parameterscan be determined, either automatically by software or by a humanoperator, based on the unprocessed data and/or the processed data fromthe CAS message file). In other words, the unprocessed data and/orprocessed data can be analyzed to determine that additional parametricdata is needed from the aircraft 110 to identify one or more sourcesthat are causing an abnormal condition that caused the CAS message fileto be generated, and the corresponding relevant parameters can then bedetermined. The analysis done to make this determination can be doneeither automatically by software that is implemented at the computer 122or can be done by an operator who is viewing the unprocessed data and/orthe processed data via the computer 122. In other words, the parameterfile will not always be generated every time it is received at thecomputer 122. Rather, the parameter file will only be generated when itis determined (either automatically by computer software or by anoperator), based on the unprocessed data and/or the processed data, thatadditional data or information is required from the aircraft to properlyassess or evaluate the cause or source of the CAS message file. Forexample, when it is determined that additional data or information isneeded from the aircraft 110, the relevant parameters corresponding tothat additional data or information can be selected or identified(either automatically or manually) at event 525.

At 530, a parameter request message can be generated that includes aparameter file that specifies the relevant parameters that are to bemeasured and recorded at the aircraft to provide the additionalparametric data, and optionally a duration value for each relevantparameter. Each relevant parameter can influence or affect data that isto be measured. Each duration value specifies how long parametric datafor that particular relevant parameter are to be measured and recorded.

In some embodiments, the parameter file can be generated automaticallyby computer software that is implemented at a computer 122. In anotherembodiment, an operator at computer 122 manually generates the parameterfile by selecting relevant parameters that are to be included in theparameter file. As will be explained below, the data for each of theserelevant parameters will eventually be measured at the aircraft and sentback to the ground from the aircraft.

In one embodiment, the parameter request message is a relatively smallmessage, such as a text message. The number of relevant parametersspecified in the parameter file can be relatively large. For instance,in one embodiment, the parameter file can specify up to 50 differentrelevant parameters that data is to be measured and recorded for at theaircraft 110. In addition, the parameter file may also specify how longdata for each of the relevant parameters are to be measured at theaircraft.

At event 540, the parameter request message can be transmitted to theaircraft 110. In one embodiment, the computer 122 communicates theparameter request message to the server 118, which then communicates itto a ground-based computer of a ground support network 116. The groundsupport network 116 then communicates the parameter request message tothe gateway 114, which communicates the parameter request message via asatellite communication link 113 to the satellite 112. The satellite 112then communicates the parameter request message to the aircraft 110 viaanother satellite communication link 111.

In accordance with some embodiments, the parameter request message canautomatically be transmitted whenever it is generated. In accordancewith some of the other disclosed embodiments, the decision as to whetheror not transmit the parameter request message can be made by an operatoror other personnel at the computer 122. When an operator at computer 122decides that the parameter request message should be communicated backto the aircraft 110 to retrieve additional data, the operator sends viathe computer interface of computer 122 a command to communicate theparameter request message to the server 118.

At event 550, an on-board computer at the aircraft 110 receives theparameter request message and extracts the parameter file from theparameter request message, and then determines requested relevantparameters specified in the parameter file (and optionally correspondingduration values that each of the requested relevant parameters should bemeasured and recorded for).

At event 560, an on-board computer at the aircraft 110 generates a datafile. In one embodiment, the data file can be generated by measuringparametric data for relevant parameters (e.g., that is received over adata bus from various sensors or other on-board computers) for acorresponding duration value and then recording the measured parametricdata in the data file at the on-board computer. In some implementations,data can be measured for a duration that is specified in the parameterfile for that particular relevant parameter. In one embodiment, themeasured parametric data for each of the relevant parameters comprises adata stream for that particular relevant parameter that is measured fora particular corresponding duration value.

In one embodiment, the on-board computer at the aircraft 110automatically creates or generates the data file by recording measureddata for each of the relevant parameters (specified in the parameterfile) in a data file. The data that is measured can be provided to theon-board computer, for example, from various sensors or other on-boardcomputers over a bus. In general, data for each of the relevantparameters can be measured for relatively longer duration in comparisonto the duration that other data is measured, for example, whengenerating the CAS message files. For example, in one embodiment, thedata for each relevant parameter can be recorded for time period betweenfive and 120 seconds in duration. The size of the data file can berelatively large in comparison to the size of the parameter file. Forinstance, in one embodiment, the data file can be between 25 KB and 250KB in size.

At event 570, the aircraft 110 communicates the data file to thecomputer 122. In the particular embodiment illustrated in FIG. 5B, theaircraft 110 communicates the data file over the first satellitecommunication link 113 to the satellite 112, the satellite 112communicates the data file over the second satellite communication link111 to the gateway 114, which then communicates the data file to theground support network 116. The ground support network 116 communicatesthe data file to the server 118, and the server 118 communicates thedata file to the other computer 122 for display on a computer interface.

Once the data file is received at the computer 122, at 580, the datafile can be processed either automatically by software or manually. Insome embodiments, it can be determined whether the measured data foreach relevant parameter is within one or more threshold limits or istrending away from a normal value. In some embodiments, an abnormalcondition is detected when the measured data for a relevant parameter isdetermined to be outside of the one or more threshold limits.Information comprising each of the particular relevant parameters thatare determined to have measured data that is outside of the particularthreshold associated with that particular relevant parameter can then beanalyzed to determine what source(s) are causing the measured data to beoutside one or more threshold limits.

Thus, method 500 can be used to detect/identify/observe an abnormalityin an aircraft sub-system (or components thereof), and toisolate/identify the underlying cause(s) of that abnormality (e.g.,pinpoint the source(s) that are causing the abnormal condition).

The flowchart that is illustrated in FIG. 5A is exemplary, and issimplified for sake of clarity. In some implementations, additionalblocks/tasks/steps can be implemented even though they are notillustrated for sake of clarity. These additional blocks/tasks/steps mayoccur before or after or in parallel and/or concurrently with any of theblocks/tasks/steps that are illustrated in FIG. 5A. It is also notedthat some of the blocks/tasks/steps illustrated in FIG. 5A may beoptional and do not need to be included in every implementation of thedisclosed embodiments. In some implementations, although notillustrated, the presence or absence of certain conditions may need tobe confirmed prior to execution of a block/task/step or prior tocompletion of a block/task/step. In other words, a block/task/step mayinclude one or more conditions that are to be satisfied beforeproceeding from that block/task/step to the next block/task/step of FIG.5A. For example, in some cases, a timer, a counter or combination ofboth may execute and need to be satisfied before proceeding to the nextblock/task/step of the flowchart. As such, any block/task/step can beconditional on other blocks/tasks/steps that are not illustrated in FIG.5A.

It is also noted that there is no order or temporal relationship impliedby the flowcharts of FIG. 5A unless the order or temporal relationshipis expressly stated or implied from the context of the language thatdescribes the various blocks/tasks/steps of the flowchart. The order ofthe blocks/tasks/steps can be varied unless expressly stated orotherwise implied from other portions of text.

In addition, in some implementations, FIG. 5A may include additionalfeedback or feedforward loops that are not illustrated for sake ofclarity. The absence of a feedback or a feedforward loop between twopoints of the flowchart does not necessarily mean a feedback orfeedforward loop is not present between the two points. Likewise, somefeedback or feedforward loops may be optional in certainimplementations. Although FIG. 5A is illustrated as including a singleiteration this does not necessarily imply that the flowchart does notexecute for a certain number of iterations or continuously or until oneor more conditions occur.

Examples of Relevant Parameters Associated with Some Aircraft Systemsand Sub-Systems

The systems and methods that are described above can be designed toacquire relevant parameters that can be used to analyze at least thevarious aircraft sub-systems (or components thereof) that are describedabove. Some specific non-limiting examples of relevant parameters willnow be given for context.

Examples of relevant parameters can include date and time stamps,hydraulic pressures, valve positions, temperatures, quantities, rates,flap positions, altitude, altitude rate airspeed, acceleration,positional information (latitude and longitude), air temperature, totalfuel, ice detection, landing gear, gear door position, aircraft weight,landing gear weight on wheels sensor, landing gear and flap handleposition, and status parameters, availability or status of a particularcommunication link channel, main and backup battery charge, temperature,voltage, current, main and backup transformer rectifier unit voltage,load, frequency, external power voltage, load, frequency, auxiliarypower unit voltage, load, frequency, transformer rectifier unit (TRU)voltage, load, integrated drive generator (IDG) frequency, load factors,voltage, APU door indicators, APU door actuators, APU speeds, fuel flow,valve positions, voltages, APU door position, turbine gas temperatures,vibrations, N1, N2 speeds, valve positions, oil pressures, temperatures,fuel flow, temperatures, pressure ratios, aileron and/or aileron trimtab movement, variables such as initial +, − movement of the aileron,initial +, − movement of the aileron trim tab, a position differencebetween the left and right aileron, a position difference between theleft and right aileron trim tab, pilot input versus actual movement ofthe left or right aileron, and pilot input versus actual movement of theleft or right aileron trim tab, roll angles, rudder and trim movement,initial +, − movement of the rudder, initial +, − movement of the trim,a position difference between the rudder pedal position and the actualrudder position, a position difference between pilot input versus actualmovement of the aileron, a position difference between pilot inputversus actual movement of the rudder, yaw angles, rudder pedal position,forces, rudder trim position, servo drum positions, trim positions,landing gear information parameters, flap positions, the time betweencommanding the flaps to a position and the flaps attaining thatposition, a position difference between the right flap position and theleft flap, flap handle position, spoiler positions, speed brake handleposition, initial +, − movement of the horizontal stabilizer position,thrust reverser position and the time it takes the thrust reverser tostow and deploy, engine data, fuel flow, thrust reverser positions,flight control surface position, servo clutch states, pilot, copilotcolumn forces, servo drum positions, trim positions, landing gearposition and other information parameters, flight control computerstatus bits, the elevator and/or elevator trim tab movement, variablessuch as initial +, − movement of the elevator, initial +, − movement ofthe elevator trim tab, a position difference between pilot input versusactual movement of the elevator trim tab, a position difference betweenpilot input versus actual movement of the elevator, pitch angles, atemperature difference between the temperature when the wing anti-icesystem was turned off and a temperature when the wing anti-ice systemwas turned on, and motor torque and current (wing) or pressure (cowl)versus temperature, wing anti-ice temperature, motor currents, icedetection status, cowl anti-ice pressures, wing, cowl anti-ice onstatus, differences among the air data probes including angle of attackfor all probes, angle of sideslip for all probes, static, total pressurefor all probes, impact pressure, AOA Miscompare CAS message data,temperatures of Enhanced Vision System (EVS) sensors, video validparameters, temperature sensor information, elapsed time for the cameraand EVS processor, etc.

CONCLUSION

The disclosed methods and systems provide a mechanism for requesting anaircraft to measure additional parametric data from on-board aircraftsystems, and for providing that measured parametric data to aground-based support network and associated ground-based computers toaid in aircraft health and trend monitoring. The disclosed methods andsystems can be used to request measurement of relevant parameter datafor various aircraft components and sub-systems on-demand and in realtime without flight crew intervention. By communicating the relevantparameter data from the aircraft to the ground systems, a more detailedanalysis of the data acquired from the aircraft can be performed andcorrective actions can be taken. The disclosed methods and systems candetect degradation of performance of an aircraft's various componentsand sub-systems and that can identify the specific source of a potentialfault within particular components and sub-systems of the aircraft. Thedisclosed methods and systems can reduce the amount of time needed toidentify and diagnose problems and perform routine troubleshooting andaircraft maintenance tasks. In-flight issues can be identified forground-based crews as soon as they occur to facilitate the developmentand implementation of quick and efficient return-to-service when theaircraft lands. The precise source of technical issues on the aircraftcan be identified much more rapidly, and the time spent in conductingaircraft maintenance tasks can be significantly reduced. In addition,potential problems with a particular sub-system can be identified beforethat sub-system fails.

Those of skill in the art would further appreciate that the variousillustrative logical blocks/tasks/steps, modules, circuits, andalgorithm steps described in connection with the embodiments disclosedherein may be implemented as electronic hardware, computer software, orcombinations of both. Some of the embodiments and implementations aredescribed above in terms of functional and/or logical block components(or modules) and various processing steps. However, it should beappreciated that such block components (or modules) may be realized byany number of hardware, software, and/or firmware components configuredto perform the specified functions. To clearly illustrate thisinterchangeability of hardware and software, various illustrativecomponents, blocks, modules, circuits, and steps have been describedabove generally in terms of their functionality. Whether suchfunctionality is implemented as hardware or software depends upon theparticular application and design constraints imposed on the overallsystem. Skilled artisans may implement the described functionality invarying ways for each particular application, but such implementationdecisions should not be interpreted as causing a departure from thescope of the present invention. For example, an embodiment of a systemor a component may employ various integrated circuit components, e.g.,memory elements, digital signal processing elements, logic elements,look-up tables, or the like, which may carry out a variety of functionsunder the control of one or more microprocessors or other controldevices. In addition, those skilled in the art will appreciate thatembodiments described herein are merely exemplary implementations

The various illustrative logical blocks, modules, and circuits describedin connection with the embodiments disclosed herein may be implementedor performed with a general purpose processor, a digital signalprocessor (DSP), an application specific integrated circuit (ASIC), afield programmable gate array (FPGA) or other programmable logic device,discrete gate or transistor logic, discrete hardware components, or anycombination thereof designed to perform the functions described herein.A general-purpose processor may be a microprocessor, but in thealternative, the processor may be any conventional processor,controller, microcontroller, or state machine. A processor may also beimplemented as a combination of computing devices, e.g., a combinationof a DSP and a microprocessor, a plurality of microprocessors, one ormore microprocessors in conjunction with a DSP core, or any other suchconfiguration. The word “exemplary” is used exclusively herein to mean“serving as an example, instance, or illustration.” Any embodimentdescribed herein as “exemplary” is not necessarily to be construed aspreferred or advantageous over other embodiments.

The steps of a method or algorithm described in connection with theembodiments disclosed herein may be embodied directly in hardware, in asoftware module executed by a processor, or in a combination of the two.A software module may reside in RAM memory, flash memory, ROM memory,EPROM memory, EEPROM memory, registers, hard disk, a removable disk, aCD-ROM, or any other form of storage medium known in the art. Anexemplary storage medium is coupled to the processor such the processorcan read information from, and write information to, the storage medium.In the alternative, the storage medium may be integral to the processor.The processor and the storage medium may reside in an ASIC.

In this document, relational terms such as first and second, and thelike may be used solely to distinguish one entity or action from anotherentity or action without necessarily requiring or implying any actualsuch relationship or order between such entities or actions. Numericalordinals such as “first,” “second,” “third,” etc. simply denotedifferent singles of a plurality and do not imply any order or sequenceunless specifically defined by the claim language. The sequence of thetext in any of the claims does not imply that process steps must beperformed in a temporal or logical order according to such sequenceunless it is specifically defined by the language of the claim. Theprocess steps may be interchanged in any order without departing fromthe scope of the invention as long as such an interchange does notcontradict the claim language and is not logically nonsensical.

Furthermore, depending on the context, words such as “connect” or“coupled to” used in describing a relationship between differentelements do not imply that a direct physical connection must be madebetween these elements. For example, two elements may be connected toeach other physically, electronically, logically, or in any othermanner, through one or more additional elements.

While at least one exemplary embodiment has been presented in theforegoing detailed description, it should be appreciated that a vastnumber of variations exist. It should also be appreciated that theexemplary embodiment or exemplary embodiments are only examples, and arenot intended to limit the scope, applicability, or configuration of theinvention in any way. Rather, the foregoing detailed description willprovide those skilled in the art with a convenient road map forimplementing the exemplary embodiment or exemplary embodiments. Itshould be understood that various changes can be made in the functionand arrangement of elements without departing from the scope of theinvention as set forth in the appended claims and the legal equivalentsthereof.

What is claimed is:
 1. A method, comprising: generating a parameterrequest message that includes a parameter file that specifies therelevant parameters to be measured at an aircraft; communicating theparameter request message to the aircraft over satellite communicationlinks; measuring data for each relevant parameter and recording themeasured data in a data file at the aircraft; and communicating the datafile from the aircraft to a ground-based computer.
 2. A method accordingto claim 1, further comprising: processing, at the ground-basedcomputer, data transmitted from an aircraft that is in flight; providingthe processed data to another computer that is remote from theground-based computer and coupled to the ground-based computer; anddetermining, based on the processed data, relevant parameters to bemeasured at the aircraft.
 3. A method according to claim 2, wherein theaircraft has a plurality of sub-systems, and further comprising:generating, at the aircraft that is in flight, a crew alerting system(CAS) message file that comprises unprocessed data, wherein the CASmessage file automatically indicates that measured data for a sub-systemof the aircraft is outside one or more threshold limits and that anabnormal condition has been detected; opening a first satellitecommunication link between the aircraft and the satellite and a secondsatellite communication link between the satellite and a ground-basedgateway; communicating the CAS message file from the aircraft over thefirst satellite communication link to the satellite; communicating theCAS message file from the satellite over the second satellitecommunication link to the gateway; and communicating the CAS messagefile from the gateway to a ground support network that includes theground-based computer; and wherein the step of processing, at aground-based computer, data that was transmitted from an aircraft thatis in flight, comprises: processing, at the ground-based computer, theunprocessed data from the CAS message file to generate the processeddata.
 4. A method according to claim 3, wherein the step of providingthe processed data to another computer that is coupled to theground-based computer, comprises: communicating the processed data fromthe ground-based computer of the ground support network to a server thatserves as a portal to the ground support network; and communicating theprocessed data from the server to the computer
 122. 5. A methodaccording to claim 4, wherein the step of determining, based on theprocessed data, relevant parameters that are to be measured at theaircraft, comprises: determining, based on analysis of the processeddata, that additional parametric data is needed from the aircraft toidentify one or more sources that are causing an abnormal condition andthat caused the CAS message file to be generated, and determiningrelevant parameters, corresponding to the additional parametric data,that are to be measured at the aircraft to provide the additionalparametric data.
 6. A method according to claim 2, wherein the step ofcommunicating the parameter request message to the aircraft oversatellite communication links, comprises: communicating the parameterrequest message to a server; communicating the parameter request messagefrom the server to a ground-based computer of a ground support network;communicating the parameter request message from the ground supportnetwork to a gateway; communicating the parameter request message fromthe gateway via a satellite communication link to the satellite; andcommunicating the parameter request message to the aircraft via anothersatellite communication link.
 7. A method according to claim 2, whereinthe parameter file comprises: the relevant parameters that are to bemeasured and recorded at the aircraft to provide the additionalparametric data, wherein each relevant parameter is influences oraffects data that is to be measured by the aircraft; and a durationvalue for each relevant parameter, wherein each duration value specifieshow long parametric data for that particular relevant parameter are tobe measured and recorded.
 8. A method according to claim 7, wherein thestep of measuring data for each relevant parameter and recording themeasured data in a data file, comprises: receiving, at an on-boardcomputer of the aircraft, the parameter request message; extracting theparameter file from the parameter request message at the on-boardcomputer of the aircraft, and from the parameter file, determining therelevant parameters and the corresponding duration values for each ofthe relevant parameters; and measuring parametric data for each relevantparameter for a corresponding duration value and recording the measuredparametric data in the data file at the on-board computer, wherein themeasured parametric data for each of the of relevant parameterscomprises a data stream for that particular relevant parameter that ismeasured for a particular corresponding duration value.
 9. A methodaccording to claim 1, wherein communicating the data file from theaircraft, comprises: communicating the data file from the aircraft overthe first satellite communication link to the satellite; communicatingthe data file from the satellite over the second satellite communicationlink to the gateway; communicating the data file from the gateway to theground support network; communicating the data file from the groundsupport network to a server; communicating the data file from the serverto the other computer for display on a computer interface; and furthercomprising: using the measured data for each of the relevant parametersto identify the one or more sources that are causing an abnormalcondition, wherein the abnormal condition is detected when the measureddata is determined to be outside of the one or more threshold limits.10. A system, comprising: a gateway; an aircraft; a satellite that iscommunicatively coupled to the aircraft and the gateway via satellitecommunication links; a ground support network comprising a ground-basedcomputer; and a computer, coupled to the ground-based computer, that isconfigured to generate a parameter request message that includes aparameter file that specifies relevant parameters that are to bemeasured at the aircraft, and to communicate the parameter requestmessage to the gateway for transmission to the aircraft over satellitecommunication links; wherein the aircraft comprises: an on-boardcomputer that is configured to measure data for each relevant parameterof the parameter file and to record the measured data in a data file;and a transceiver configured to transmit the data file to the satellitefor delivery to the other computer.
 11. A system according to claim 11,wherein the aircraft has a plurality of sub-systems, and wherein thedata transmitted by the aircraft while in flight comprises a crewalerting system (CAS) message file generated by the on-board computerthat comprises the unprocessed data, wherein the CAS message fileautomatically indicates that measured data from a sub-system of theaircraft is outside one or more threshold limits and that an abnormalcondition has been detected, and wherein the on-board computer isconfigured to open a communication path that includes a first satellitecommunication link between the aircraft and the satellite and a secondsatellite communication link between the satellite and a ground-basedgateway, and to communicate the CAS message file from the aircraft overthe first satellite communication link to the satellite, and wherein thesatellite is configured to communicate the CAS message file over thesecond satellite communication link to the gateway, and wherein thegateway is configured to communicate the CAS message file to a groundsupport network that includes the ground-based computer.
 12. A systemaccording to claim 12, wherein the ground-based computer of the groundsupport network is configured to process the unprocessed data from theCAS message file to generate the processed data, and to communicate theprocessed data to a server that serves as a portal to the ground supportnetwork and communicates the processed data to the other computer.
 13. Asystem according to claim 13, wherein the relevant parameters aredetermined based on analysis of the processed data, and correspond toadditional parametric data that is needed from the aircraft to identifyone or more sources that are causing an abnormal condition and thatcaused the CAS message file to be generated, wherein each relevantparameter influences or affects data that is to be measured by theaircraft.
 14. A system according to claim 11, wherein the parameterrequest message is communicated to the aircraft over satellitecommunication links by communicating the parameter request message to aserver, communicating the parameter request message from the server tothe ground support network, communicating the parameter request messagefrom the ground support network to the gateway, communicating theparameter request message from the gateway via the second satellitecommunication link to the satellite; and communicating the parameterrequest message to the aircraft via the first satellite communicationlink.
 15. A system according to claim 11, wherein the parameter filecomprises: the relevant parameters that are to be measured and recordedat the aircraft to provide the additional parametric data; and aduration value for each relevant parameter, wherein each duration valuespecifies how long parametric data for that particular relevantparameter are to be measured and recorded.
 16. A system according toclaim 16, wherein the on-board computer of the aircraft, after receivingthe parameter request message, is configured to extract the parameterfile from the parameter request message at the on-board computer of theaircraft, to determine the relevant parameters and the correspondingduration values for each of the relevant parameters from the parameterfile, to measure parametric data for each relevant parameter for acorresponding duration value and to record the measured parametric datain the data file, wherein the measured parametric data for each of theof relevant parameters comprises a data stream for that particularrelevant parameter that is measured for a particular correspondingduration value.
 17. A system according to claim 11, wherein thetransceiver is further configured to communicate the data file over thefirst satellite communication link to the satellite, wherein thesatellite is configured to communicate the data file over the secondsatellite communication link to the gateway, wherein the gateway isconfigured to communicate the data file to the ground support network,wherein the ground support network is configured to communicate the datafile to a server, and wherein the server is configured to communicatethe data file to the other computer for display on a computer interface.18. A computer, comprising: a processor that is configured to performprocessing to: generate a parameter request message comprising aparameter file that specifies relevant parameters that are to bemeasured at an aircraft and recorded in a data file, and communicate theparameter request message for transmission to the aircraft oversatellite communication links.
 19. A computer according to claim 19,wherein the parameter request message is generated in response toprocessed data that was received from the aircraft while in flight,wherein the relevant parameters are determined and selected based onanalysis of the processed data, and correspond to additional parametricdata that is needed from the aircraft to identify one or more sourcesthat are causing an abnormal condition, wherein each relevant parameterinfluences or affects data that is to be measured by the aircraft.